EP0039731B1 - Flow device for sensors - Google Patents

Flow device for sensors Download PDF

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Publication number
EP0039731B1
EP0039731B1 EP19800902351 EP80902351A EP0039731B1 EP 0039731 B1 EP0039731 B1 EP 0039731B1 EP 19800902351 EP19800902351 EP 19800902351 EP 80902351 A EP80902351 A EP 80902351A EP 0039731 B1 EP0039731 B1 EP 0039731B1
Authority
EP
European Patent Office
Prior art keywords
bore
fluid
housing
flow
passageway
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP19800902351
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0039731A1 (en
EP0039731A4 (en
Inventor
Richard V. Deleo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rosemount Inc
Original Assignee
Rosemount Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rosemount Inc filed Critical Rosemount Inc
Publication of EP0039731A1 publication Critical patent/EP0039731A1/en
Publication of EP0039731A4 publication Critical patent/EP0039731A4/en
Application granted granted Critical
Publication of EP0039731B1 publication Critical patent/EP0039731B1/en
Expired legal-status Critical Current

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
    • G01K13/028—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow for use in total air temperature [TAT] probes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
    • G01K7/16—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements
    • G01K7/18—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements the element being a linear resistance, e.g. platinum resistance thermometer

Definitions

  • This invention relates to a device for measuring a parameter of a fluid stream, for example for measuring the temperature of the air stream flowing past an air vehicle in flight.
  • a device for measuring a parameter of a fluid stream comprising an elongate housing having a bore for flow of the fluid stream therethrough, the housing having a leading portion at a first fluid stream inlet end of the bore and a trailing portion at a second fluid stream outlet end of the bore; a plurality of ports from the bore to the exterior of the housing in the leading portion for providing boundary layer control; an annular fluid passageway in the housing downstream of the ports and coupled to and outboard of the bore and connected to the exterior of the housing to cooperate with the bore to provide a lower pressure area for fluid which flows through the annular fluid passageway; and sensor means to measure the parameter, the sensor means being supported in the annular fluid passageway between its coupling to the bore and its connection to the exterior of the housing.
  • an essential feature of the device disclosed therein is that the bore through the housing be unobstructed, and to encourage fluid flow from the bore into the annular fluid passageway containing the sensor means, the exterior of the housing is shaped specifically to provide a suction effect to the exterior of the housing.
  • This specific shaping is disadvantageous with regard to cost and base of manufacture of the device, and can have adverse effects in the overall boundary layer control for the device.
  • such a known device is characterised by restriction means in the bore downstream of the coupling to the annular fluid passageway to provide internal regulation of the flow of the fluid stream through the bore.
  • the device of this invention has the advantages that the flow regulation provided by the restriction means enhances the operation of the device at Mach numbers above 0.5, while avoiding the disadvantages of the known device discussed above.
  • US-A-3170328 discloses the use of a restrictor means in a bore in a device for measuring a parameter of a fluid stream flowing in the bore, the restrictor means serving to provide internal flow regulation.
  • the bore also contains the sensor means measuring the parameter, and this prior specification teaches that such an arrangement is essential there being no disclosure or suggestion of locating the restriction means other than in the bore containing the sensor means.
  • the device of this invention when the fluid stream is air, Mach number regulation in the bore is provided. Regulation of the rate of flow internal to the device enhances operation at higher ambient flow rates. For example, for operation in air at higher subsonic Mach numbers, e.g. above Mach 0.5 poor overall performance such as poor accuracy and repeatability, is avoided. Selection of a restriction means to regulate the internal rate of flow for air to a Mach number between 0.1 and 0.5 has resulted in enhanced performance. Further, the restriction means raises the internal pressure so that routing of a portion of undisturbed fluid to the sensor means in the annular fluid passageway is more easily accomplished. Because of porting of fluid from the bore for boundary layer control, the sensor means is subjected to relatively undisturbed, free stream fluid parameters such as temperature which, for example, is raised substantially adiabatically upon impingement on the sensor means.
  • a particular advantage is that since the internal pressure is raised due to the restriction means, it is not necessary for the external shape of the housing to increase in diameter rearwardly as required for the device of US--A-4.,152,938.
  • the internal pressure is raised considerably above the local static pressure and, hence, flow is more easily induced into the annular fluid passageway and to the sensor means.
  • the raised internal pressure compared to the local static pressure enables porting of the first passageway to the exterior of the device from an area of constant diameter.
  • the fluid stream may be moving relative to the device which can be in a fixed location such as in a gas conduit, wind tunnel or the like, or the device may be mounted on an air vehicle, such as an aircraft, missile, helicopter, or the like, with such air vehicle moving through the fluid or air mass.
  • the device which can be in a fixed location such as in a gas conduit, wind tunnel or the like, or the device may be mounted on an air vehicle, such as an aircraft, missile, helicopter, or the like, with such air vehicle moving through the fluid or air mass.
  • FIG. 1 and Figure 2 A first preferred embodiment of a device for measuring a parameter in a fluid stream is shown in Figure 1 and Figure 2 and is generally indicated at 10.
  • Device 10 includes a housing 11 which is formed of two main housing elements connected together, a leading portion 12 and a trailing portion 14 which together form the elongate shape of device 10.
  • a strut 15 connected to trailing portion 14 supports device 10 in a desired position relative to a flow stream.
  • Leading portion 12 is cast or formed from a cylindrical block of metal.
  • a flow face 16 is contoured to provide a relatively,sleek aerodynamic shape and to reduce drag.
  • a central, relatively uniform bore 18 is made substantially along the axis of the housing 11 for flow therethrough.
  • Leading portion 12 has an inlet port for fluid flow, which flow is indicated as left to right by the arrow in Figure 1. Bore 18 through trailing portion 14 is the main outlet for fluid flow.
  • BLC boundary layer control
  • Trailing portion 14 is also cast or formed from a metal block, and has a first end 25 and an outlet end 27.
  • the first end 25 of trailing portion 14 is suitably dimensioned to be inserted into a large bore 26 in leading portion 12 thus forming an annular passageway open to bore 18 through an annular inlet 24.
  • Leading portion 12 and trailing portion 14 are connected together in a conventional manner as bywelding, brazing orthe like where surfaces of the two overlap as at 28.
  • Ports 22 are spaced closely upstream from annular inlet 24 and the flow through ports 22 urges the lighter particles of the flow, for example, the molecules forming air, to change direction more than the heavier particles such as the suspended solids, raindroplets or the like. Similarly, the lighter particles tend to flow into the annular inlet 24 from bore 18.
  • a first annular passageway 32 is formed by casting or machining in trailing portion 14 radially outboard of bore 18.
  • Passageway 32 has a plurality of ports 34, preferably six, which are angled from the longitudinal or flow axis. Ports 34 are located near the maximum exterior diameter of trailing portion 14, but may exhaust parallel to the longitudinal or flow axis. Passageway 32 then cooperates with bore 18, inlet 24 and ports 34 as well as ports 22 to provide a relatively undisturbed flow of fluid through passageway 32.
  • An inner surface 36 of passageway 32 has a sensor element 38 disposed thereon.
  • a sensor is shown in Figure 3.
  • An insulator layer 40 such as mica is first disposed on surface 36.
  • An element 38 which preferably is a platinum wire resistor, is then wrapped over insulator 40 and a second layer of an insulator 42 is then disposed on element 38.
  • an outer tube 44 is slid or drawn over the entire element 38. Tube 44 may then be mechanically or hydrostatically swaged onto element 38 to further improve ruggedness and response time. Conventional treatment to hermetically seal element 38 is also provided.
  • Suitable leadwires 45 and 46 are then conventionally connected to ends of sensor 38 respectively in a flow direction longitudingally aft of sensor 38 in trailing portion 14. As best shown in Figure 1, leadwires 45 and 46 are then routed through a central cavity 47 in strut 15 to a desired interface connection 48 or 49 respectively. Other sensors such as pyrometers, thermocouples, humidity sensors, pressure sensors or the like and known mounting methods for such sensors may be used. Sensor 38 is mounted in position before housing portions 12 and 14 are joined together.
  • Sensing element 38 embodies this construction, which provides a substantially greater expected life than bare wire sensors. Response time and ruggedness of sensor 38 is improved by swaging tube 44.
  • An annular (tubular) separator 50 is formed in trailing portion 14. Separator 50 provides an outboard barrier 52 for first passageway 32 and radiation shielding for sensor 38. Separator 50 in cooperation with the large bore 26 of leading portion 12 also forms a second annular passageway 54 in device 10. Second passageway 54 exhausts to the exterior through a plurality of ports 56, preferably six. Ports 56 are located somewhat aft of the longitudinal midpoint of device 10. Passageway 54 in cooperation with the fluid stream in bore 18, inlet 24, and ports 56 provides a third path forthefluid stream flow. Passageway 54 further urges the flow into inlet 24 and provides further BLC so that the flow reaching sensor 38 is relatively undisturbed having substantially free stream flow characteristics.
  • trailing portion 14 is an assembly comprised of separator 50 which has a cylindrical shape and is brazed to trailing portion 14 at 50A, then the tube 38A which has sensor 38 mounted on its inner surface 36 is brazed to trailing portion 14 at 38B.
  • a restriction means or sonic throat 60 is formed at outlet end 27 of trailing portion 14 by welding or brazing a suitable metal insert 62 to the inner wall of bore 18, thus reducing the effective inside diameter of bore 18 at outlet end 27.
  • Insert 62 on its flow facing side is formed to have a taper 64 from bore 18 to the reduced diameter of insert 60 to reduce turbulence in the flow caused by insert 60.
  • the diameter of bore 18 was 6 millimeters and the minimum diameter of insert 60 was 5 millimeters and the maximum diameter of the device was 118 millimeters, thus regulating the rate of flow of air for higher subsonic Mach numbers of air flow to Mach 0.35 in bore 18. It is understood that other bore and insert diameters for regulation to other selected flow rates for other fluids or other Mach numbers for air are determined using conventional calculation methods.
  • restriction means or throat 60 regulates the rate of fluid flow through device 10 and raises the internal pressure in bore 18 to further urge flow through both ports 22 and inlet 24, and through passageways 32 and 54. This increased internal pressure urging the flow through such ports and passageways enhances conditions so that fluid reaching sensor 38 has parameters substantially similar to the fluid stream in an undisturbed and uncontaminated state.
  • This embodiment both takes advantage of the device of US-A-4152938 by routing heavier particles in the fluid through bore 18, while diverting only relatively undisturbed free stream fluid to the sensor 38. Restriction means or throat 60 enhances the capability of device 10 to divert the fluid with minimal disturbance or turbulence added thereto.
  • flow face 16 of leading portion 12 has an electrical heating element 80 therein for anti-icing.
  • Cavity 47 in strut 15 is shown with leadwires 45 and 46 and heating element 80 therein.
  • the heating element 80 comprises two conductors with a resistance therebetween. The conductors are held at different potentials and hence a current flows through the resistance thus generating heat for anti-icing.
  • Other conventional heating elements such as coils, resistors or the like may be used.
  • heating element 80 is conventionally disposed in flow face 16 in leading portion 12, and also in cavity 47 near the leading edge of strut 15 to provide anti-icing on such leading edge, and may also be disposed in outlet end 27 or other areas of device 10 for anti-icing as desired.
  • flow face 16 of leading portion 12 is shown as somewhat more blunt than as shown in Figure 1.
  • cavity 47 in strut 15 is shown with leadwires 45 and 46 and a conduit 90 for carrying hot gas, such as engine bleed air from a jet engine compressor of an air vehicle, or rocket exhaust gas or the like, which conduit 90 is provided to conduct heat to flow face 16 for anti-icing.
  • Conduit 90 preferably is routed through the leading edge of strut 15 to provide anti-icing there also.
  • Conduit 90 is coupled to an annular cavity 92 in leading portion 12 in which the hot gas circulates to heat flow face 16. The hot gas is then exhausted through a suitable configuration of hot gas ports 94. If desired, such hot gas may also be routed to outlet end 27 or other areas of housing 11.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Measuring Volume Flow (AREA)
  • Measuring Temperature Or Quantity Of Heat (AREA)
EP19800902351 1979-11-05 1980-10-31 Flow device for sensors Expired EP0039731B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US9117979A 1979-11-05 1979-11-05
US91179 1979-11-05

Publications (3)

Publication Number Publication Date
EP0039731A1 EP0039731A1 (en) 1981-11-18
EP0039731A4 EP0039731A4 (en) 1984-09-05
EP0039731B1 true EP0039731B1 (en) 1987-02-04

Family

ID=22226471

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19800902351 Expired EP0039731B1 (en) 1979-11-05 1980-10-31 Flow device for sensors

Country Status (4)

Country Link
EP (1) EP0039731B1 (enrdf_load_stackoverflow)
JP (1) JPS6332130B2 (enrdf_load_stackoverflow)
DE (1) DE3071905D1 (enrdf_load_stackoverflow)
WO (1) WO1981001331A1 (enrdf_load_stackoverflow)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3878373D1 (de) * 1987-09-29 1993-03-25 Kwc Ag Elektrisch gesteuerte mischarmatur.
FR2808874B1 (fr) * 2000-05-15 2002-07-26 Auxitrol Sa Capteur pour la mesure de parametres physiques sur un flux de fluide et notamment capteur de temperature d'air degivre
US7014357B2 (en) 2002-11-19 2006-03-21 Rosemount Aerospace Inc. Thermal icing conditions detector
US7175136B2 (en) 2003-04-16 2007-02-13 The Boeing Company Method and apparatus for detecting conditions conducive to ice formation
US7031871B2 (en) 2004-06-04 2006-04-18 Rosemount Aerospace, Inc. Sensor assembly for determining total temperature, static temperature and Mach number
US7331421B2 (en) 2005-03-30 2008-02-19 The Boeing Company Flow restrictors for aircraft inlet acoustic treatments, and associated systems and methods
US20160238456A1 (en) * 2015-02-12 2016-08-18 Rosemount Aerospace Inc. Air temperature sensor and fabrication
DE102017205573A1 (de) * 2017-03-31 2018-10-04 Rolls-Royce Deutschland Ltd & Co Kg Messvorrichtung und Messverfahren für eine Strömung

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2588840A (en) * 1946-09-07 1952-03-11 Lockheed Aircraft Corp Temperature probe
US2970475A (en) * 1956-10-08 1961-02-07 Rosemount Eng Co Ltd Gas temperature probe
US2931227A (en) * 1957-07-22 1960-04-05 Frank D Werner Gas temperature probe
US3170328A (en) * 1961-06-13 1965-02-23 Frank D Werner Total temperature probe
US3512414A (en) * 1968-05-23 1970-05-19 Rosemount Eng Co Ltd Slotted airfoil sensor housing
US4152938A (en) * 1978-05-19 1979-05-08 Karl Danninger Aircraft temperature probe

Also Published As

Publication number Publication date
JPS6332130B2 (enrdf_load_stackoverflow) 1988-06-28
JPS56501465A (enrdf_load_stackoverflow) 1981-10-08
DE3071905D1 (en) 1987-03-12
EP0039731A1 (en) 1981-11-18
WO1981001331A1 (en) 1981-05-14
EP0039731A4 (en) 1984-09-05

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